Propeller mechanism for aircraft.



w. c. WHITTEMORE aw. E. HAMM. PROPELLER IVIECHANISNI FOR AIRCRAFT.

APPLICATION FILED APR. 8. I9I 5 u 1,288,336. ,n Patented Dec. 17, 1918.

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W. C. WHITTEMORE & W. E. HAMM.

PROPELLER MECHANISM FOR AIRCRAFT.

APPLICATION FILED APR.8.1916.

Patented Dec. 17, 1918.

3 SHEETS-SHEET 2.

l l/ll/ W. C. WHITTEMORE 6L W. E. HAMM.

PROPELLER MECHANISM FOR AIRCRAFT.

APPLICATION FILED APR. 8| I9I6.

Patented Dec. 17, .1918.

3 SHEETS-SHEET 3.

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UNITED STATES PATENT oFnIcE.

WINTHROP C. WHITTEMORE, OF MEDFIELD, AND WALTER E. HAMM, OF BOSTON, MASSACHUSETTS,ASSIGNORS TO WHITTEMORE HAMM COMPANY, OF BOSTON, MASSACHUSETTS, `A CORPORATION OF MASSACHUSETTS.

PROPELLER MECHANISM FOR AIRCRAFT.

To all wlw/1t z'z may concern.'

Be it known that we, lVIN'rHnoP C. lVHrr- Timon-E and lVaLTER E. HAMM, both citizens of the United States, and residents of-Medfield, in the county of Norfolk and State of Massachusetts, and Boston, in the county Of Suffolk and State of Massachusetts, respectively, have invented' new and useful lmprovements in vPropeller Mechanism for Aircraft, of which the following is a specification.

This invention relates to propel-ler mechanism for air craft, and its principal object is to improve the construction and efficiency of aeroplanes, whether ef the monoplane type, the biplane or other multiplane type, the tandem plane type, or other types, by revolving the propeller or propellers aroundv the fuselage, so-called, that is, around the main structure which connects the planes or supportingsurfaces with the rudder and elevator, or steering surfaces, such structure consisting of two or more Then the fuselage is covered with a shell or casing, or

when it consists of a shell with or without an internal frame or reinforcing elements, the propeller is revolved around the shell.

Many advantages are gained by this construction. The propeller may be placed at th'e'rear of the trailing edge of the supporting planes and back of the seat for the aviator and passengers. Thus, their view is not obstructed by the propeller and they are not in the path of air currents created by the propeller. The propeller thrust may lbe applied at approximately the center of resistance of the fuselage. A gun maybe placed in advance of the propeller, the recoil of which will act along the line of the center of thrust of the propeller, thereby reducing the tendency of making the aeroplane unstableby the discharge of the gun. When the fuselage is covered' with a tapering or spindledilre shell or casing. the current of air from the propeller impinging upon the tapering bodyl will act to the advantage of forward motion, thereby in a measure counterz'icting head resistance. All the rods, cables. control wires. ete.. may run through the propeller bearing or ringto the rudder. eleva or and other steering mechanisms. The

Specication of Letters Patent.

Patented Decul, 1918.l

Application :nea April s, 1916.- seriai no. 89,943.

propeller is in a safer and more protected position, and it may be supplemented if desired by a second propeller arranged on the front end of the'machine in the usual manner.l acting as a tractor. while our framef encircling propeller acts as al pusher. In such case there'might be two-independent motors or power plants, the center of thrust of both of which could be in a direct line.

In the accompanying drawings which illustrate the invention,-

Figure l is an elevation of the mechanism, showing the relation of propeller, aeroplane framework, .and propeller drive;

Fig. 2 isa vertical central section through line 2*2 of Fig. l;

Fig. 3 is a section on line 3-3 of. F ig. 1;

Fig. et is a detail in section on line 4-4 of Fig. l;

Fig. 5 is a detail in section on lineI 5-5 of Fig. 1;

Fig. 6 is a detail view ofiadj-u'stment` means of one of the propeller bla-des from the top of Fig. l;

Figs. 7 and 8 are )detail sections corresponding to the lower part of Fig. 2 showing modifications of the bearings for the internal gear propeller ring;

Figs. 9. 11. 1S and 15, illustrate in section and in side elevation various forms of gearing for propeller drives; A

Figs. 10, 12, 1l and 16 are diagrammatic elevations of said drives, respectively;

Fig. 17 is a side view of a monoplane; and

Fig. 18 is a sideiview of a biplane, embodyingthe invention.

Referring first to Figs. 1,. Q and 8. the struct-ure for carrying the propeller and the propeller driving mechanism, comprises the two disk-like castings 6,6, made with marginal rims or flanges to which the shell or. casing of the aeroplane body is secured at each side of the structure. Boxes or sockets 7 are formed in said castings. through which extend the longerons ormain members F (9) of the frame. Said sockets 7 correspond in number and `position to the three main lengthwise extending' frame members F of the body of the aeroplane. Said frame members constitute the main framework of the machine. termed the fuselage. which may be covered by a casing or shell S (Figs. 17 and` viewed ioo 18) forming a tapering or spindle-like body, and which carries the engine, the supporting planes 9, and` the rudder and elevator, or steering surfaces,10...l There ma)7 of course be other braces or struts such as a (Fig. 17

for reinforcing the body, outside of the periphery of the 4castings 6. and ntsurround# ries two or more propeller blades 13, thev stems or Shanks of which` 18, are angularljyY adjustable by a rack 1l and pinion 15, the rack lbeing operated b v an adjusting' screw 1G mounted to turn in a box 15 secured to ring 11.

The propellers and propeller ring 11 revolve around the castings (3 and the fuselage, and the endwise thrust is received by antifriction bearings. such vas ball bearings 17. ln the form shown in Fig. 2 the balls run in a race\ Yavv in a bearing ring 1S mounted on the casting. In the. form shownin Fig. 7 there is also a racewav in the side of the propeller ring 1.1, and in the form shown ln Fig. 8 a series of lball bearing rollers 1f) -a're mounted on the casting to engage each side of the propeller ring. In either case an annular shield or easing 20, constituting an oil retainer secured to ring 11, covers and protects the bearings. and prevents the throwing off of oil bv centrifugal action.

ln the form shown in Figs. 1. 2, 9 and 1() the propeller ring 11, is driven by a main central gear wheel 21 and three intermediate gear wheels or pinions 22,which mesh with gear wheel :1.1 and the internal gear12 of the propeller ring. The gear wheel 21 is suitably jourualed in ball bearings Q3 held in `iournal boxes formed on the castings ti. and

is keyed to a driving shaft 2:1, which is revolved b v the engine. Similarlythe pinions 22 are journaled in ball bearings held in journal boxes formed on the castings f3. The cast-ings are identical and are fastened together b v bolts 26 with the several gear wheels held between them.

'.Ihe lulu-icatiou-of the device ma)y be understood bv reference to Figs. 1 to ()il is introduced into bearing 23 from any suitable source of supptv`l thronghqipe 31 (Fig. `l`). From bearing Ql the oil is distrilmtcd eentrifugally between the casting disks (i, to pinions Q2 and their bearings. and thence to the internal gear 1l and laairings 1T, and collected in the oil receiver 20., A\ pipe or duet 32 leads from the space within the oil receiver lll back to the center bearing :113. and a yspring pressed wiper tFig. Slengages the flange 34 of the oil receiver 20, which revolvesvwith the ring 1l. and directs -the oil back through pipe 32 to the center bearing where it is used over again.

In the modifi ation shown in Figs. 11 and 12. the propeller ring is driven by intermediate gears 29., as before,and said gears z2 are driven b v a central gear 21 fast on the short shaft 2T. Gear :8 is also sec-ured to shaft 27 and is driven b v gear wheel 25) fast on driving shaft 24.

In the form shown in Figs. 13 and 1l, gear wheel 30 n driving sha-ft 2=li.`meshes directl)7 with the internal gear on ring 11.

`In the form shown in Figs. 15 and 1G the ring 11 is provided with an external gear 31. which is'driven by a gear wheel 32 fast on driving shaft 24 which is outside of the. fuselage.. Shaft QA!" may be connected bv gearing. belt, or other suitable driving mechanism `to ay motor.

`The castings G, 6, are provided with suitable holes 35 (Figs. 1 and 3) through which the cont-rol wires or cables 36, pass from the aviators position forward of the propellers to the, rudder and other steering or controlling devices. There may be as many holes as desired (two are herein shown) and there may be as man)7 control members 3G `as required for the particular steering mechanisin used (three on each side being herein shown). Said control members thus all pass through the propeller bearing or ri ng.

From the foregoing it will be seen that the propeller revolves around the fuselage at the rear of the vaviators seat, and at the rear of the supporting` planes. b'v which we mean the supporting .planes 9 when ma-y chines of the type shown in Figs. 17 and 1S are used, or the forward planes in ease the invention is applied to a machine having forward yand rear planes arranged tendem fashion. Also in the preferred form the propeller revolves around the tapering shell of `the fuselage whereby `the current of' air from the propelle acts on the tapering shell. innnediately at the rear ofthe propeller and so contributes to theforward propulsion of the machine.

lVe claim:

l. 1n an aeroplane having the shell of its fuselage transversely divided into two parts and having a propeller arranged to rotate in the plane of the division, the combination of front and rear disk-like members disposed in spaced relationship between said two parts of the fuselage` flanges on the front and rear disks respectively extending forwardly and rearwardly along the shell of the fuselage on each sidey of said division` the iauges being secured to the two portions of the shell. means for rigidl)y attaching the two disks together. and means disposed between the disksI for rotating' the propeller.

2. ln an aeroplane having the shell of its l Si l) e the front and rear members respectively to 'in spaced relationship between said two parts of the. fuselage, means for connecting the front and rear portions of the fuselage, means for connect-ing the two disks together at a plurality of points intermediate their centers and peripheries, and means disposed between said members for rotating the propeller.

3. An aeroplane comprising a fuselage. two disk-like members dispose-d transverselY of the fuselage in spaced relationship, a propeller arranged to rotate around the fuselage in the region of said disks. and gears jour naled in said disks for rotating said propeller.

Ji. An' aeroplane. comprising' a/fuselage, a propeller adapted'to rotate around the fuselage` the propeller comprising' a` ring and blades secured thereto. roller bearings disposed on each side of said ring in engagement with the ring, the axes ofthe bearings being disposedpbliquely with respect to the plane of the propeller so that the bearings position the propeller both laterally and radially.

An aeroplanecomprising a fuselage shell, the shell being transverselyy divided into two parts with a gap therebetween. a disk disposed on each side of said gap, peripheral flanges on the disks secured to the two portions of the shell respectively, a propeller adapted to rotate around said gap, an intel'- nal gear on the propeller, a shaft journaled in said disks concentrically with said internal gear, an external gear mounted on said shaft between said disks, and a plurality of gears journaled in said disks in engagement with said internal and external gears.

6. An aeroplane comprising a fuselage, a propeller including a ring and blades secured thereto, means for rotating said ring about the fuselage, and means extendin from said ring into juxtaposition to the Vuselage to prevent oil being thrown outwardly from said rotating means.

7. An aeroplane comprising a fuselage, a. propeller including' a ring and blades secured thereto, means for rotating said ring about the fuselage, and means extending from, said ring into juxtaposition to the fuselage to trap the oil thrown outwardly from said'rotating means, and means automatically to conduct the oil back to the rotating means. l

8. In an aeroplane having its ,fuselage transversely divided into two parts, the combination of a propeller ar anged to rotate about'the fuselage at the division between the two parts` means for rotatably supportmg the propeller, and means overhanging the space between the two parts of the fuselage to prevent oil being thrown outwardly fromsaid means.

9. In an aeroplane having a propeller arranged to rotate about the fuselage between the main aerofoils and the tail control aerofoils. the combination of diskdike niembers disposed in juxtaposed relationship on opposite sides of the transverse plane of the propellerl respectively, and means for driving said propeller associated with said disks, said disks having alined. openings therein adapted to permit the longerons of the fuselage to extend'continuously therethrough.

10. In an aeroplane having the shell of its fuselage transversely divided into two parts and having a propeller arranged to rotate in the plane of the division, the combination of disk-like members disposed in spaced relationship in the opposed ends oi the divided fuselage, means for securing said members to the respective parts of the fuselage along their outer peripheries, an interna-l gear disposed inthe peripheral region of said .disks for driving' the propeller, an external gear disposed between saidl disks and concentrically therewith, a plurality of `intermediate gears connecting said external gear with said internal gear, said intermediate gears being spaced about the annular' space between the internal and external gea-rs` and said disks having a plurality'of alined openings spaced about said annular space between said intermediate gears to rcce-ive the fuselage longerons` whereby the longerons may extend continuously through said disks from one part of the 'fuselage to the other part.

11. In an aeroplane having the shell of its fuselage transversely divided into two parts and having a propeller arranged to rotate in the plane of the division, the combination ofrineans within the fuselage for driving the propeller, means for rigidly connecting said two parts of the fuselage together, and means for controlling the aeroplane rudder extending across the space between said two parts 0f the fuselage within the contines of. the fuselage. said driving means and connecting means being so arranged as not to interfere with the control means.

12. In an aeroplane having a propeller arranged to rotate about the, fuselage between the main aerofoils and the tail con-A trol aerofoils, the combination of an internal gear for driving the propeller, drive gearing for transmitting power from the engine to said internal gear. and means for'controlling the control surfaces in the rea-r of the propeller, said control means extending through said internal gear at a point orpoints radially displaced from the axis of its fuselage transversely divided into tWoblo0 parts and having a propellerarranged to rotate in the plane 01"' the division, the coinbination of disk-like members disposed in spaced relationship in the opposed ends of the divided fuselage, means for securing said members to the respective parts of the fuselage aloneT their oute ',periplieries, an in ternal gear disposed in the peripheral region of said disks for driving' the propeller, a central external gea-r disposed between said disks and concentrically therewith, a pluI rality of intermediate gears connecting said external gear with said internal gear, said intermediate gears being' spaced about the annular space between the. internal and eX- 15 ternal gears, said disks having' one or more alined openings disposed in said annular space between said intermediate gears, and means for controlling' the control surfaces in the rear of the propeller, said control means extending' through said openings across the space ybetween the two parts ot the fuselage.

Signed by us at Bostonl` Massachusetts. this third dai,v of April. 1916.

WINTHROP C. lV ll l'lTlCM( )it IC. WALTER E. HAMM. 

